EP1176297A1 - Rotierende turbobrennkraftmaschine - Google Patents

Rotierende turbobrennkraftmaschine Download PDF

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Publication number
EP1176297A1
EP1176297A1 EP00935751A EP00935751A EP1176297A1 EP 1176297 A1 EP1176297 A1 EP 1176297A1 EP 00935751 A EP00935751 A EP 00935751A EP 00935751 A EP00935751 A EP 00935751A EP 1176297 A1 EP1176297 A1 EP 1176297A1
Authority
EP
European Patent Office
Prior art keywords
rotor
guide
wall
rotary
flaps
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Granted
Application number
EP00935751A
Other languages
English (en)
French (fr)
Other versions
EP1176297B1 (de
EP1176297A4 (de
Inventor
Jury Mikhailovich Luzhkov
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
Otkrytoe Aktsionernoe Obschestvo "aljulkasaturn"
Borovichsky Kombinat Ogneuporov OAO
Original Assignee
Otkrytoe Aktsionernoe Obschestvo "aljulkasaturn"
Borovichsky Kombinat Ogneuporov OAO
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by Otkrytoe Aktsionernoe Obschestvo "aljulkasaturn", Borovichsky Kombinat Ogneuporov OAO filed Critical Otkrytoe Aktsionernoe Obschestvo "aljulkasaturn"
Publication of EP1176297A1 publication Critical patent/EP1176297A1/de
Publication of EP1176297A4 publication Critical patent/EP1176297A4/de
Application granted granted Critical
Publication of EP1176297B1 publication Critical patent/EP1176297B1/de
Anticipated expiration legal-status Critical
Expired - Lifetime legal-status Critical Current

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Classifications

    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00—Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/04—Charge admission or combustion-gas discharge
    • F02B53/08—Charging, e.g. by means of rotary-piston pump
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02B—INTERNAL-COMBUSTION PISTON ENGINES; COMBUSTION ENGINES IN GENERAL
    • F02B53/00—Internal-combustion aspects of rotary-piston or oscillating-piston engines
    • F02B53/02—Methods of operating
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T10/00—Road transport of goods or passengers
    • Y02T10/10—Internal combustion engine [ICE] based vehicles
    • Y02T10/12—Improving ICE efficiencies

Definitions

  • the invention relates to internal combustion engines, in particular to rotary engines whose working members make oscillatory motions about an axle fixed on a rotor.
  • a rotary internal combustion engine comprising a rotor having radial-longitudinal posts and longitudinal blades swivel-mounted in the area of their external diameter, which blades have carriers that contact a guiding means, the rotor being positioned in a cylindrical body limited at its end faces by lateral walls and having an inlet opening and an outlet opening, a working chamber being defined by the external surface of a longitudinal blade, the cylindrical surface of the body and by the lateral walls of the body.
  • a coaxial driven shaft is provided having additional radial posts and bell cranks articulated to the rotor working blades.
  • the air in the engine is compressed by rotation of adjacent blades of the rotor and rotation of the driven shaft about the posts when a cam is subjected to being rolled upon by a follower roller of the adjacent blades' articulation.
  • a drawback of the known invention is the presence of an auxiliary driven shaft, which, furthermore, rotates at a variable velocity with respect to the driver shaft rotation angle, which makes the construction of this device complex. It should be noted that in this solution, as in many internal combustion engines, only the exterior side of the blades (one side of a cylinder in piston internal combustion engines) participates in the work cycle. From the point of view of the work cycle, the space under the blades is not utilized.
  • a rotary internal combustion engine that comprises a rotor having longitudinal flaps that are swivel-mounted thereon in the area of the external diameter along its rotation axis and separate one from another the spaces arranged therein on both sides of each of the flaps, and which rotor is installed in a cylindrical body on whose end face wall is disposed a closed oval-shaped guide in contact with the carriers of the flaps, and a conduit for gas-exchange between the spaces located on both sides of the flaps.
  • the end face surfaces of the flaps and the surfaces of adjacent posts that contact the end face surfaces of the flaps are conjugated, contact one another, each of the flaps separating the compression space from the working space. Suction and exhaust openings are provided.
  • a feature of this solution that is advantageous is that both sides of a flap participate in the work cycle of the engine, one side participating as a compression space wall, the other participating as a working space wall.
  • the carrier pins are fixed to flaps (made as an integral part of the flaps) and transmission of the working forces to the engine is effected through these pins, then their design has to be stronger and they necessarily have to be positioned on both sides of the flaps. Otherwise, if the pins are positioned on only one side, they have to be made much bigger, which will result in increased leakage. Furthermore, in the case where the pins are disposed on one side of a flap end face, the flap may be affected by skewness, seizure, and even a failure of the engine may occur. Strengthening the pins and increasing the rigidity of the flaps by increasing their size is also unacceptable here, since this will result in a reduction of the working volumes of the engine.
  • the object of the invention is to create a guide of such a shape, that it, while providing good smoothness of travel of a carrier thereon, would be simple to manufacture with high quality of the working surfaces. Achievement of this object makes it possible to obtain high frequencies of engine rotor rotation.
  • Additional objects of the invention are to create normal working conditions for the carrier-guide pair as regards temperature, lubrication quality, and, furthermore, to obtain a torque on the engine rotor that is also due to the reactive force obtained during waste gas exhaust (by use of a turbo-effect).
  • a rotary-turbine internal combustion engine comprising a rotor having longitudinal flaps that are swivel-mounted on the rotor in the area of the external diameter along its rotation axis and separate one from another the spaces arranged therein on both sides of each flap, the rotor being positioned in a cylindrical body on whose end face wall is arranged a closed guide in contact with carriers of the flaps, and a conduit for gas-exchange between the spaces disposed on both sides of the flaps, a guide therein and disposed on the end face wall of the body being made as an annular guide, and its longitudinal axis is set with an eccentricity relative to the rotation axis of the rotor.
  • the annular guide is made in a floating ring that is coaxial with the guide and is positioned on the end face wall of the body.
  • the invention is novel in that the guide, disposed on the end face wall of the body, is made annular and its longitudinal axis is set with an eccentricity relative to the rotation axis of the rotor, the guide may be made in a floating ring that is coaxial with the guide and is positioned on the end face wall of the body, for example in the form of a groove extending to the end face of the floating ring.
  • Making the guide annular makes it possible to attain the maximally high frequencies of rotation of the rotor in such an engine, which frequencies are attained owing to smoothness of the rolling motion of the guide profile and owing to the quality of the working surfaces of the guide. High precision in manufacturing, high surface finish, quality of the surface layer in respect to hardness and coatings are easily ensured in this case.
  • each carrier in the form of a crank positioned outside the side wall of the rotor, one end of the crank contacting the guiding groove, both the crank itself and the point of contact with the guide will be located in the zone of relatively low temperatures, which makes it possible to organize reliable oil cooling in this location.
  • the lateral wall of the rotor now reliably covers the high temperature zone.
  • the second end face wall of the body becomes a portion of the spaces above and under each of the flaps, and therefore it is easy to make the suction opening, having the required working area, and also the inlet and outlet of the gas-exchange conduit on that wall.
  • a single end face wall of the unit is obtained. Having such a single end face wall of the unit, which wall is in direct contact with two rotors composing a single whole, and directing the eccentricities of the longitudinal axes of the guides of these engines in directions that are opposite to the axis of rotation of the rotors, a virtually balanced system of two rotors will be provided.
  • a space is formed, by means of which the precompression pressure in the space under the flap may be adjusted.
  • This pressure must be selected during operational development of an engine, taking into account that this pressure should be minimal because energy is consumed, but should be sufficient to provide guaranteed blowing of the waste gases from the space above the flap and filling it with clean air.
  • a rotary-turbine internal combustion engine comprises a rotor 1 having longitudinal flaps 2 attached using swivels 3 in the area of the external diameter of the rotor 1 along its axis of rotation 4.
  • Each flap 2 separates a space 5 under a flap and a space 6 above the flap, one from the other.
  • the rotor 1 is mounted in a cylindrical body 7, on whose end face wall 8 is arranged a closed annular guide 9 that contacts carriers 10 of flaps 2.
  • the longitudinal axis 11 of the guide 9 is mounted with an eccentricity "e" relative to the axis of rotation 4 of rotor 1.
  • the longitudinal axis 11 of the guide 9 is shifted vertically upwards with respect to the axis of rotation 4 of the rotor 1, although as regards the engine, the direction of eccentricity is of no importance.
  • a second end face wall of the body 7 is made in the form of a removable cover 12 that is in direct contact with an end face 13 of the rotor 1, has a suction opening 14 disposed in an angular position in the area of the maximal shift of the profile of the guide 9 with respect to the axis of rotation 4 of the rotor 1 and connected to the spaces 5 under the flaps 2.
  • the suction opening 14 can be arched and extended in the direction opposite to the direction of rotation of the rotor 1.
  • a conduit 15 for carrying out gas exchange between spaces 4 and 5 is also provided in the cover 12.
  • An inlet 16 of the gas-exchange conduit 15 is positioned opposite the space 5 under the flap 2 in the area of its minimal distance from the axis of rotation 4 of the rotor 1, and an outlet 17 is positioned opposite the space 6 above the flap 2.
  • the inlet 16 and the outlet 17 of the gas exchange conduit 15 are disposed in an angular position in the area of the minimal shift of the profile of the guide 9 with respect to the axis of rotation 4 of the rotor 1.
  • the other end face of the rotor 1 is provided with an end face wall 18.
  • Each carrier 10 that serves for rotating its flap 2 with respect to the swivel 3, is made in the form of a crank 19 located off the wall 18 and rigidly connected to the flap 2 in the area of the swivel 3 so that both the crank 19 and the flap are capable of rotating about an axis 20 of the swivel 3.
  • the guide 9 is in contact with another end 21 of the crank 19.
  • the annular guide 9 may be made in the form of a groove 22 in a floating ring 23 that is coaxial with the guide and positioned with respect to its internal diameter on a wear-resistant adapting bushing 24 which in turn is rigidly attached on the end face wall 8 of the body 7.
  • the annular groove 22 has two annular working surfaces 25 and 26 which are in contact with the ends 21 of the crank 19.
  • An oil space 27 is formed between the wall 18 of the rotor 1 and the end face wall 8 of the body 7.
  • the ports 28 are coupled to oil-delivering ports 29 of the body 7, which in turn are coupled to an oil-supply system.
  • a spark plug 31 is mounted on the body 7 inside it and opposite the spaces 6. The plug is mounted in an angular position in the area of the maximal shift of the profile of the guide 9 with respect to the axis of rotation 4 of the rotor 1.
  • Two engines are easily arranged as an integral unit.
  • two separate engines face one another by the covers 12, which covers in this case form an integral end face wall 32.
  • Eccentricities "e” of the longitudinal axes 11 of the guides 9 of these two engines are directed in directions opposite to the axis of rotation 4 of the rotor 1.
  • the unit has a common oil space 33, and its two rotors have a common shaft 34.
  • An additional space 37 communicating with the space 5 and having on its wall a through opening 38 that communicates with the inlet 16 of the gas-exchange conduit 15, may be formed on the wall 36 of the rotor 1, under each flap 2.
  • the inlet 16 of the gas-exchange conduit on the cover 12 may be provided with a segment groove 39 directed in the direction opposite to the direction of rotation of the rotor 1.
  • the rotor 1 on its external diameter may be provided with a wall 40 in which tangential openings 41 are made in the form of, for example, slot nozzles.
  • the annular guide 9 may also be made in the simplest way, in particular, in the form of an annular groove 42 on the end face wall 8 of the body 7 (Fig. 1).
  • the engine operates in the following manner.
  • the space 5 which at that moment contains the air compressed therein is in a position opposite the inlet 16 of the gas-exchange conduit 15, and this air, via the conduit 15 and through its outlet 17, enters the space 6 that has, at that moment, maximum volume and, consequently, minimum pressure.
  • the waste gas is pushed out of the space 6, and the space is filled with clean air from the space 5.
  • the displaced gas, via the exhaust opening 30, is discharged into the atmosphere.
  • compression of the air in the space 6 begins and the air compressed to maximum is situated in the uppermost point. Atmospheric air is drawn into the space 5 via the arched suction opening 14.
  • the flap 2 is once again in the uppermost point and the work cycle repeats. Since there are relatively many flaps on an engine, there are as many cycles during one rotation of the rotor as there are flaps on the rotor.
  • gas from the space 6 that is subjected to blowing and the air that performs the blowing and comes from the space 5 with the rotor 1 in the lowest position are directed to the tangential openings 41 in the wall, creating the "turbine" effect in the rotor and obtaining an additional torque on the rotor.
  • the unit consisting of two engines, facing one another via the covers 13 and forming in that case an integral end face wall 32, works so that when the rotors rotate, their forced disbalances are directed in opposite directions, and a virtually balanced system of two rotors is obtained.
  • the necessity of installing two flywheels-counterbalances, as, for example, in the Wankel engine, is obviated.
  • the additional space 37 formed on the wall 36 of rotor 1 under each flap 2 and having a through opening 38 which communicates with the inlet 16 of the gas-exchange conduit 15, controls, by its volume, the precompression that takes place in the space 5 under the flap 2.
  • the annular guide makes it possible for the crank to move smoothly on its high-quality working surface, which makes it possible to obtain a sufficiently high frequency of rotation of the rotor.
  • a cycle of a two-stroke engine having an excellent system for blowing the waste gases, filling the working spaces with clean air, and furthermore having precompression, is easily effected.
  • the title of the invention is a rotary-turbine engine.

Landscapes

  • Engineering & Computer Science (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Supercharger (AREA)
  • Engine Equipment That Uses Special Cycles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Nitrogen And Oxygen Or Sulfur-Condensed Heterocyclic Ring Systems (AREA)
  • Retarders (AREA)
EP00935751A 2000-03-01 2000-03-01 Rotierende turbobrennkraftmaschine Expired - Lifetime EP1176297B1 (de)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
PCT/RU2000/000068 WO2001065086A1 (fr) 2000-03-01 2000-03-01 Moteur a combustion interne a turbine et rotor

Publications (3)

Publication Number Publication Date
EP1176297A1 true EP1176297A1 (de) 2002-01-30
EP1176297A4 EP1176297A4 (de) 2002-05-29
EP1176297B1 EP1176297B1 (de) 2004-06-09

Family

ID=20129487

Family Applications (1)

Application Number Title Priority Date Filing Date
EP00935751A Expired - Lifetime EP1176297B1 (de) 2000-03-01 2000-03-01 Rotierende turbobrennkraftmaschine

Country Status (16)

Country Link
US (1) US6457450B1 (de)
EP (1) EP1176297B1 (de)
JP (1) JP3626455B2 (de)
KR (1) KR100514231B1 (de)
CN (1) CN1120294C (de)
AU (1) AU748386B2 (de)
BR (1) BR0007208A (de)
CA (1) CA2349154C (de)
CZ (1) CZ296876B6 (de)
DE (1) DE60011422T2 (de)
EA (1) EA200000636A1 (de)
ES (1) ES2226847T3 (de)
IL (1) IL143364A0 (de)
MY (1) MY126839A (de)
UA (1) UA51850C2 (de)
WO (1) WO2001065086A1 (de)

Families Citing this family (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20040089251A1 (en) * 2001-04-02 2004-05-13 Talero John Alejandro Sanchez Water cooled rotary internal combustion machine
JP3809837B2 (ja) * 2001-05-26 2006-08-16 ヒョン キム，ドン ロータリー機関
TW561217B (en) * 2003-03-03 2003-11-11 Tsung-Yun Chen Rotary engine
US20040261731A1 (en) * 2003-06-27 2004-12-30 Hojjat Fathollahi Rotary engine and compressor
US20060130803A1 (en) * 2004-12-21 2006-06-22 Chun-Lin Tseng Multiple-power engine device
US7343894B2 (en) * 2005-10-16 2008-03-18 Enrique Haluy Leon Modular rotary engine
US8177536B2 (en) 2007-09-26 2012-05-15 Kemp Gregory T Rotary compressor having gate axially movable with respect to rotor
CN101215990B (zh) * 2007-12-27 2011-06-22 黄天山 摆动活塞式转子发动机
US8733317B2 (en) * 2009-12-14 2014-05-27 Gotek Energy, Inc. Rotary, internal combustion engine
RU2451801C2 (ru) * 2010-06-22 2012-05-27 Юрий Яковлевич Дьяченко ДВУХОСЕВОЙ РОТОРНО-КАМЕРНЫЙ ДВИГАТЕЛЬ ВНУТРЕННЕГО СГОРАНИЯ (ДоРК ДВС)
CN103075248B (zh) * 2013-01-09 2015-04-08 黄荣嵘 涡轮转子节能发动机
CN111771061B (zh) 2017-12-13 2023-02-10 益班修科技股份有限公司 旋转式流体流动装置
US11168683B2 (en) 2019-03-14 2021-11-09 Exponential Technologies, Inc. Pressure balancing system for a fluid pump
US11428156B2 (en) 2020-06-06 2022-08-30 Anatoli Stanetsky Rotary vane internal combustion engine

Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1349353A (en) * 1918-07-17 1920-08-10 Jr Oscar Howard Wilber Rotary engine
FR574199A (fr) * 1923-11-27 1924-07-07 John A Morgan Machinery Compan Machine rotative utilisable comme moteur, ou comme pompe, ainsi que pour d'autres usages

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1400255A (en) * 1920-07-16 1921-12-13 Henry D Anderson Rotary internal-combustion motor
US1458361A (en) * 1920-10-11 1923-06-12 Roto Pump Mfg Co Rotary pump
US2121660A (en) * 1935-03-20 1938-06-21 Christian M Jespersen Internal combustion motor
FR2121906A5 (de) * 1971-01-11 1972-08-25 Woywode Karl
US3871337A (en) * 1972-09-05 1975-03-18 Edward Howard Green Rotating cylinder internal combustion engine
US3971347A (en) 1973-10-10 1976-07-27 Michael Vasilantone Rotary internal combustion engine
US4072132A (en) * 1976-08-27 1978-02-07 Mighty-Mini Rotary Engine, Limited Rotary internal combustion engine
DE2919417C3 (de) * 1979-05-15 1982-03-11 Helmut 2300 Kiel Gerthe Rotationskolben-Brennkraftmaschine
EP0103985A3 (de) * 1982-08-20 1985-02-20 Mack H. Williams Rotierende Maschine oder Kompressor
SU1518555A1 (ru) * 1987-01-22 1989-10-30 Всесоюзный научно-исследовательский институт природных газов Роторный двигатель внутреннего сгорани
FR2651828A1 (fr) * 1989-09-11 1991-03-15 Lassee Guy Moteur a piston rotatif.
IT1252762B (it) * 1991-07-04 1995-06-28 Lando Baldassini Variatore di velocita' rotatoria e lineare per motori a due tempi applicabile all'albero motore.
US5261365A (en) * 1992-05-26 1993-11-16 Edwards Daniel J Rotary internal combustion engine
DE4225932C2 (de) * 1992-08-03 1995-09-14 Scheidecker Gisela Gertrud Drehkolben-Brennkraftmaschine

Patent Citations (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US1349353A (en) * 1918-07-17 1920-08-10 Jr Oscar Howard Wilber Rotary engine
FR574199A (fr) * 1923-11-27 1924-07-07 John A Morgan Machinery Compan Machine rotative utilisable comme moteur, ou comme pompe, ainsi que pour d'autres usages

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of WO0165086A1 *

Also Published As

Publication number Publication date
CA2349154A1 (en) 2001-09-03
WO2001065086A8 (fr) 2002-01-24
MY126839A (en) 2006-10-31
UA51850C2 (uk) 2002-12-16
DE60011422T2 (de) 2005-06-09
DE60011422D1 (de) 2004-07-15
CA2349154C (en) 2002-12-10
AU748386B2 (en) 2002-06-06
EP1176297B1 (de) 2004-06-09
CN1341192A (zh) 2002-03-20
EP1176297A4 (de) 2002-05-29
JP2003525383A (ja) 2003-08-26
AU5116600A (en) 2001-09-12
CZ20011854A3 (cs) 2001-12-12
EA001184B1 (ru) 2000-10-30
JP3626455B2 (ja) 2005-03-09
CZ296876B6 (cs) 2006-07-12
US6457450B1 (en) 2002-10-01
WO2001065086A1 (fr) 2001-09-07
ES2226847T3 (es) 2005-04-01
KR100514231B1 (ko) 2005-09-13
BR0007208A (pt) 2002-04-16
EA200000636A1 (ru) 2000-10-30
KR20020004937A (ko) 2002-01-16
IL143364A0 (en) 2002-04-21
CN1120294C (zh) 2003-09-03

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